• 한국위성정보통신학회논문지
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• 제6권2호
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• pp.136-140
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• 2011

위성은 효용성 증가로 지속적인 발전를 거치며 여러 종류의 위성이 개발 및 계획이 진행되고 있으며, 여러 가지 필수적인 시스템을 포함하고 있다. 이중 전력 공급 시스템은 위성의 수명에 직접적인 영향을 가지고 있으며, 다양한 요구에 맞게 설계가 이루어 져야 하는 특성을 지니고 있다. 따라서 위성의 설계 요구조건에 부합하는 전압 변압기의 설계 및 안정한 제어가 요구된다. 일반적으로 저궤도 위성의 전력 변환은 각 모듈 및 부하에 따라 여러 단계를 거쳐 전달하게 된다. 이러한 다양한 단계의 전력 변환에 대한 분석 및 이를 반영한 설계는 복잡성으로 인해 쉽게 파악하기 힘든 특성을 가지게 된다. 본 논문에서는 간결 화된 일반화 모델링을 통한 대신호, 소신호분석으로 정 전압 변압기 설계 및 안정화 제어를 위한 방안을 제시한다.

• 대한원격탐사학회지
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• 제24권5호
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• pp.507-515
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• 2008

Many studies have generally used a large number of pure pixels as an approach to training set design. The training set are used, however, varies between classifiers. In the recent research, it was reported that small mixed pixels between classes are actually more useful than larger pure pixels of each class in Support Vector Machine (SVM) classification. We evaluated a usability of small mixed pixels as a training set for the classification of high-resolution satellite imagery. We presented an advanced approach to obtain a mixed pixel readily, and evaluated the appropriateness with the land cover classification from IKONOS satellite imagery. The results showed that the accuracy of the classification based on small mixed pixels is nearly identical to the accuracy of the classification based on large pure pixels. However, it also showed a limitation that small mixed pixels used may provide insufficient information to separate the classes. Small mixed pixels of the class border region provide cost-effective training sets, but its use with other pixels must be considered in use of high-resolution satellite imagery or relatively complex land cover situations.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2004년도 한국우주과학회보 제13권2호
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• pp.56-56
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• 2004

• 한국항해항만학회:학술대회논문집
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• 한국항해항만학회 2006년도 International Symposium on GPS/GNSS Vol.1
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• pp.141-144
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• 2006

The deviations in the injection orbital parameters, resulting from launcher dispersions, need to be estimated and used for autonomous satellite operations. For the proposed small satellite mission of the university there will be two GPS receivers onboard the satellite to provide the instantaneous orbital state to the onboard data handling system. In order to meet the power requirements, the satellite will be sun-tracking whenever there is no imaging operation. For imaging activities, the satellite will be maneuvered to nadir-pointing mode. Due to such different modes of orientation the geometry for the GPS receivers will not be favorable at all times and there will be instances of poor geometry resulting in no output from the GPS receivers. Onboard the satellite, the orbital information should be continuously available for autonomous switching on/off of various subsystems. The paper presents the strategies to make use of small arcs of data from GPS receivers to compute the mean orbital parameters and use the updated orbital parameters to calculate the position and velocity whenever the same is not available from GPS receiver. Thus the navigation message from the GPS receiver, namely the position vector in Earth-Centered-Earth-Fixed (ECEF) frame, is used as measurements. As for estimation, two techniques - (1) batch least squares method, and (2) Kalman Filter method are used for orbit estimation (in real time). The performance of the onboard orbit estimation has been assessed based on hardware based multi-channel GPS Signal simulator. The results indicate good converge even with short arcs of data as the GPS navigation data are generally very accurate and the data rate is also fast (typically 1Hz).

• 한국항공운항학회지
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• 제23권4호
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• pp.140-145
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• 2015

An on-board reaction wheel is payload of small satellite for space environment test. The reaction wheel is designed for considering physical, electrical, and environmental requirements. In this paper, we report design, manufacturing process and operation performance verification. Furthermore, the specifications of environmental test are performed under environmental conditions for guarantee of stability and reliability. The operation and environment test results are presented to meet the requirements at the reaction wheel flight model.

• International Journal of Aerospace System Engineering
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• 제5권2호
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• pp.8-15
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• 2018

For small earth observation satellites, alignment between the optical components is important for precise observation. However, satellite cameras are structurally subject to misalignment in the launch environment where vibration excitations and impacts apply, and in space environments where zero gravity, vacuum, radiant heat and degassing occur. All of these variables can cause misalignment among the optical components. The misalignment among optical components results in degradation of image quality, and a re-alignment process is needed to compensate for the misalignment. This process of re-alignment between optical components is referred to as a refocusing process. In this paper, we proposed a 3 - axis focusing mechanism to perform the refocusing process. This mechanism is attached to the back of the secondary mirror and consists of three piezoelectric inertia-friction actuators to compensate the x-axis, y-axis tilt, and de-space through three-axis motion. The fabricated focus mechanism demonstrated excellent servo performance by experimenting with PD servo control.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2005년도 Proceedings of ISRS 2005
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• pp.241-244
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• 2005

Many building detection methods mainly rely on line segments extracted from aerial or satellite imagery. Building detection methods based on line segments, however, are difficult to succeed in high resolution satellite imagery such as IKONOS imagery, for most buildings in IKONOS imagery have small size of roofs with low contrast between roof and background. In this paper, we propose an efficient method to extract line segments and group them at the same time. First, edge preserving filtering is applied to the imagery to remove the noise. Second, we segment the imagery by watershed method, which collects the pixels with similar intensities to obtain homogeneous region. The boundaries of homogeneous region are not completely coincident with roof boundaries due to low contrast in the vicinity of the roof boundaries. Finally, to resolve this problem, we set up snake model with segmented region boundaries as initial snake's positions. We used a greedy algorithm to fit a snake to roof boundary. Experimental results show our method can obtain more .correct roof boundary with small size and low contrast from IKONOS imagery. Snake algorithm, building roof detection, watershed segmentation, edge-preserving filtering

• Journal of Astronomy and Space Sciences
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• 제40권1호
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• pp.35-44
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• 2023

Surveillance and reconnaissance intelligence in the space domain will become increasingly important in future battlefield environments. Moreover, to assimilate the military provocations and trends of hostile countries, imagery intelligence of the highest possible resolution is required. There are many methods for improving the resolution of optical satellites when observing the ground, such as designing satellite optical systems with a larger diameter and lowering the operating altitude. In this paper, we propose a method for improving ground observation resolution by using an optical system for a previously designed low orbit satellite and lowering the operating altitude of the satellite. When the altitude of a satellite is reduced in a circular orbit, a large amount of thrust fuel is required to maintain altitude because the satellite's altitude can decrease rapidly due to atmospheric drag. However, by using the critical inclination, which can fix the position of the perigee in an elliptical orbit to the observation area, the operating altitude of the satellite can be reduced using less fuel compared to a circular orbit. This method makes it possible to obtain a similar observational resolution of a medium-sized satellite with the same weight and volume as a small satellite. In addition, this method has the advantage of reducing development and launch costs to that of a small-sized satellite. As a result, we designed an elliptical orbit. The perigee of the orbit is 300 km, the apogee is 8,366.52 km, and the critical inclination is 116.56°. This orbit remains at its lowest altitude to the Korean peninsula constantly with much less orbit maintenance fuel compared to the 300 km circular orbit.

• 한국항공우주학회지
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• 제38권6호
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• pp.620-628
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• 2010

소형위성은 저비용으로 단기간에 개발이 가능하기 때문에 이를 통해 폭 넓은 우주 연구를 수행할 수 있고 다양한 분야의 활용 가능하다. 소형위성은 빠른 개발이 가능한 이점이 있다. 따라서 신속 대응 우주 구현이 주목됨에 따라 소형위성의 역할이 급속히 증가하고 있다. 하지만 소형위성은 기존의 위성에 비해 크기나 전력의 제약이 많기 때문에 고성능의 안정적인 시스템을 기대하기는 어렵다. 이러한 문제점을 해결하고 빠른 개발을 위해 표준화와 모듈화 설계가 필요하다. 모듈화는 플러그 앤 플레이(Plug-and-Play)를 지원하여 수일 내에 인공위성 제작 및 시험을 가능하게 한다. 이러한 모듈 간의 원활한 데이터 통신을 위해서는 데이터 버스의 표준이 요구된다. CAN 통신 방식은 플러그 앤 플레이에 가장 효과적으로 대처 할 수 있는 통신방식으로 꼽힌다. CAN은 높은 신뢰성을 가지며 분산 시스템을 지원하여 위성의 호환성을 높여준다. 따라서 시험이 용이해지고 짧은 기간에 고성능의 안정적인 위성 개발이 가능하게 된다. 본 논문에서는 모듈화 방식의 소형위성 개발 방안에 대해 제안하고, CAN을 데이터 버스로 적용하여 소형위성 내부 데이터 인터페이스 버스를 설계하고 시험을 통해 적합성을 분석하여 기술하였다.

• 한국지리정보학회지
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• 제5권4호
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• pp.86-92
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• 2002

고해상도 위성 IRS-1C의 Panchromatic 영상 자료를 이용하여 한국 근해에서 선박의 수와 위치를 파악할 수 있는 가능성을 살펴보았다. Panchromatic 위성 영상에서 선박과 주변환경에 대한 위치, 크기, 모양, 그림자, 색조, 질감 및 모양의 공간배열, 높이와 깊이, 현황 및 연관성 등의 영상해석 요소를 활용하여 선박 모니터링의 논리적 접근기법을 연구하였다. 선박의 공간적 위치는 GCP가 없는 해상에서 영상의 중심위치 정보로부터 반경 35km내에서 지구좌표점으로 전환하였다. 선박의 크기는 선수에서 선미까지이나 선미에서 생기는 종파(following wave)와 추정 구분하여야 했다. 길이 100m를 기준으로 연근해 어선과 상선으로 구분하였다. 선박의 모양은 종파의 영향으로 영상에서 유선형이었다. 작은 구름의 경우 선박의 모양과 유사했으나, 해상에 반영된 구름의 그림자로 배와 구분할 수 있었다. 색조는 바다표면이 검은색을 띤 반면 소형선박은 밝은 흰색으로 나타났다. 바다의 거친 정도와 파도의 방향성 배열 등을 통해 파도와 선박을 구분하였다. 또한 쌍끌이 어선과 같은 조업방법이 어선의 어업별 종류를 영상에서 추정하는데 용이한 기초 연관 자료가 되었다.